A Mixing Process Influenced by Wall Jet-Induced Shock Waves in Supersonic Flow

With the development of hypersonic air-breathing propulsion systems, such as supersonic combustion ramjet (Scramjet) and rocket-based combined cycle (RBCC) engines, mixing process airstream with fuel in engine combustor has been drawing more attention. Due to compressibility effects, a condition is significantly inhibited. In present paper, novel strategy wall-jet induced shock waves (WJISW) put forward realize enhancement. The interaction between WJISW layer researched enhanced-mixing mechanism revealed, employing large eddy simulation (LES) methods. fine vortex structures flow field are well captured presented, utilizing numerical schlieren technique. Detailed visualization results indicate that low frequency can result ‘region action mode’ (RAM) never reported before. drastic dynamic behaviors including growth, deformation, distortion region undoubtedly promote upper lower streams. Reynolds stress distributions along streamwise x-direction suggest intense fluctuations be achieved WJISW. Moreover, sharp increase thickness realized region. mode decomposition (DMD) analysis show evolution dominated by WJISW, which leads coexistence both large- small-scale field. entrainment corresponding large-scale vortices nibbling obviously It suggested proposed good candidate for application Scramjet RBCC combustors.